Design and Analysis of C-D Nozzle and the Effect of Pressure Ratio on the Formation of Shock Diamonds in Conical Nozzle

The function of a rocket engine nozzle is to expand the hot engine exhaust gases down to ambient pressure, transforming thermal energy to directed kinetic energy in order to produce thrust.The main goal of every rocket engine is to generate a lot of heat and pressure and then convert that into workable thrust.The problem is most rockets don't solve pressure discrepancies at various altitudes.That causes various expansion conditions which affects the performance of the Rocket engine.The nozzle forms a large segment of the rocket engine structure, and as a whole, the performance of a rocket largely depends upon its aerodynamic design.The principal parameters in this context are the nozzle area expansion ratio and the shape of the nozzle contour.Considering nozzle design, there is an optimization nozzle shape and length, the bell-shaped or contour nozzle.The reason for this specific contour is that the expansion shock waves emanating from the nozzle throat region coincide and thus diminish the compression effects accompanying the reorientation of flow in the center region of the expansion section.A careful shaping of the nozzle contour and idealization of C-D nozzle can lead to a high gain in its performance.Our project aimed to solve for these discrepancies by Theoretical study, designing and optimizing a C-D Rocket nozzle.